Rockets for subcaliber training system for anti-tank weapon



Jan. 6, 1970 E. TREN ETAL ROCKETS FOR SUBCALIBER TRAINING SYSTEM FOR ANTI-TANK WEAPON Filed llviarch 7, 1968 affirme Mmqvesu 6*/ United States Patent Ofiice 3,487,780 Patented Jan. 6, 1970 3,487,780 ROCKETS FOR SUBCALIBER TRAINING SYSTEM FOR ANTI-TANK WEAPON Edvard Tren and Bjarne Narvesen, Raufoss, Norway Filed Mar. 7, 1968, Ser. No. 711,300 Claims priority, applicai7on6l2`lorway, Mar. 7, 1967,

1 Inf. cl. F42b 5/10 U.S. Cl. 102-49.2 2 Claims ABSTRACT F THE DISCLOSURE The present invention relates to a rocket for subcaliber training systems for an anti-tank weapon.

The object of the invention is to provide a subcaliber rocket which may be handled and operated by the soldier in the field the same way as a full caliber system.

A further object of the invention is to provided a subcaliber rocket having a rear nozzle formed to guide and stabilize the rocket during the flight.

In an embodiment of the invention a rocket for subcaliber training systems for an antitank weapon, comprises a head, a rod extending rearwardly from said head, a nozzle secured to the rear end of said rod, a number of propellant sticks of explosive arranged evenly spaced around said rod, and means at the rear end of the head anchoring the front ends of said sticks to the head. The nozzle consists of a cylindrical ring having a length at least equal to the diameter thereof, a central hub in said ring joined therewith by a web arranged near to the front end of the ring and a number of circumferentially spaced bores through said web. The central hub of the nozzle at the rear end may be provided with a bore adapted to receive a tracer with burning time sufiicient for all required ranges.

In order that the invention may be more clearly understood the same will now be described with reference to the accompanying drawing, in which FIGURE 1 is a side view partly in section of a rocket embodying the invention,

FIGURE 2 is an end view of the nozzle seen from the right hand side in FIG. 1,

FIGURE 3 is a side view of the nozzle connected to the igniter holder, partly in section, and

FIGURE 4 is a diagrammatical partly sectioned side view of a subcaliber launcher in its extended position.

The rocket according to the invention comprises a head 1, made from steel or other suitable metal, provided at its rear end with a central threaded bore 2 into which is screwed the forward threaded end of a steel rod 3 the rear end of which carries a nozzle 4.

The nozzle 4 is formed as a single piece comprising an outer cylindrical ring 5 having a length at least equal to the diameter thereof, a hub 6 extending preferably along the whole length of the ring 5 and joined therewith by a web 7 positioned near to the front end of the ring 5. The web 7 is provided with a number of circumferentially spaced bores 8 through which combustion gases can escape. The 4forward end of the hub is provided with a threaded bore 9, into which the threaded rear end of the rod 3 is secured which bore 9 at the rear part of the hub has an enlargement 10 adapted to receive a tracer (not shown) which may be secured in the rear end of the threaded bore 9.

When selecting the length of the nozzle as above stated and positioning the web adjacent the front end thereof, a circular space 11 is formed behind the bores 8, and the independent part of the ring 5 defining said space then serves to guide and stabilize the rocket during the fight.

The propellant of the rocket consists of a number, here six, sticks 12 of explosive arranged evenly spaced around the rod 3. The front ends of the sticks are inserted in corresponding bores 13 in a disc 14 which is clamped against the rear end of the head by means of a collar 15 on the rod 3. At the rear end the head is provided with a reduced portion 1a on which is slideably supported a disc 16 of a suitable plastic material, which disc together with a shoulder 17 forms a circular groove receiving an O-ring 18, the arrangement being such that when the rocket is fired the explosive pressure acts on the disc 16 which thereby exerts a compression on the O- ring to maintain an effective sealing between the head and the barrel.

The rocket is to be fired from an original rocket launcher of the type comprising first and second tubular sections 20, 21 telescopingly connected to enable them to be extended from a shortened inoperative position into an elongated operative position, firing means 22 and trigger means 23 all of which are known and form no part of the present invention.

In the embodiment of the launcher shown in the drawing, the launcher is shown for use in firing subcaliber rockets of the type above described.

To that end a rear tubular member 24 of a subcaliber adapted to the rocket is secured to the rear section 20 and is slidable in a second or for-ward tubular member 25. Said tubular members are supported coaxially in the sections 21, 22 by discs 26, 27 anchored to the sections by countersunk screws 28, 29. The rear disc 27 has a forwardly projecting breech shaped extension 30 threadedly connected to the rear end of the tubular member 24.

The igniter means 31 is secured in a holder 32 having a cylindrical portion 33 which slideably receives the rear part of the nozzle 4 and is secured thereto by a number of shear pins 34, said holder is fastened against a shoulder in the breech end of the barrel 24 by a threaded lock ring 36. A flexible tube 35 is leading from the igniter 31 to the primer chamber in the firing pin houses 22.

What we claim is:

1. A rocket 'for subcaliber training systems for an antitank weapon, comprising a head having a shoulder and a reduced portion extending therefrom at the rear end, a disc slidably supported on the reduced portion of the head, the disc and the shoulder defining a circular groove, a sealing ring in said groove, a rod extending rearwardly from said head, a nozzle secured to the rear end of said rod, a number of propellant sticks of explosive arranged evenly spaced around said rod, means at the rear end of the head anchoring the front ends of said sticks to the head, said nozzle consisting of a cylindrical ring having a length at least equal to the diameter thereof, a central hub in said ring joined therewith by a web arranged near the front end of the ring and a number of circumferentially spaced bores through said web.

2. A rocket as claimed in claim 1 in which said central hub at the rear end thereof is provided with a bore adapted t0 receive a tracer.

References Cited UNITED STATES PATENTS 3/ 1954 Abramson IGZ-49.2 9/ 1955 Garrahan H12-49.2 1/ 1963 Kallin et al 102-87 FOREIGN PATENTS 1 1/ 1941 Czechoslovakia.

U.S. Cl. X.R. 

